Transition Measurement and Prediction of a Supersonic Experimental Aircraft Wing Boundary Layer

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Through 3 years of the this research project, we have succeeded to clarify the complicated 3D transition mechanism. Especially, swept wing boundary layer transition mechanism is as follows.Stream wise stationary vortex system start to appear as the primary instability. Unsteady wave instabilities of two different frequency modes are induced by this stationary vortices. High frequency secondary instability is considered to be the key sequence for the turbulent transition. By sucking the low momentum flow selectively at the position of stationary vortices, we have succeeded to delay the transition with at least 1/3 of the suction volume compared with the uniform suction case.